Abstract: A method for checking a level of damage of at least one part of an aircraft. According to the disclosure, such a method comprises at least: a collection step for receiving data representative of measurements of at least one flight parameter, the data being generated during a mission of the aircraft by at least one embedded sensor; a projection step for projecting points onto a map in order to form an image point; an identification step for identifying, for each image point, an image zone in which the image point is located; and an analysis step for statistically analyzing the identified image zones and determining the level of damage of the at least one aircraft part.

Abstract: A suspension device provided with at least one suspension means. The suspension means comprise a tuned mass damper, the damper comprising an inertial mass carried by a mass support. The suspension means include at least a first actuator generating a dynamic force for acting on the swinging motion of the damper. The inertial mass being movable longitudinally in translation relative to the mass support, the suspension device including a second actuator connected to the inertial mass to move the inertial mass longitudinally relative to the mass support.

Abstract: A rotorcraft tail rotor comprising at least two blade elements, each blade element being suitable for pivoting about a collective pitch variation axis Z in order to vary the collective pitch of each blade element of the tail rotor, each blade element including at least one compensation weight comprising a projection emerging substantially perpendicularly to a main inertia axis of the blade element, the main inertia axis being parallel to a longitudinal direction of the blade element. In the invention, the tail rotor is wherein the compensation weight includes a deformable portion that is movable relative to the projection in a plane P that is parallel to the main inertia axis of the blade element.